General Electric Company

Jeffrey Carl Mayer

John Alan Manteiga

Brian Benscoter Roberts

Apostolos Pavlos Karafillis

Gary Charles Liotta

Craig Douglas Young

John Howard Starkweather

Ivan Elmer Woltmann

Frank Anthony Lastrina

Kenneth Arthur Gould

Leslie M Pommer

Courtney Ann Kiszewski

Antonio C Gominho

Kyle Earl Roland Henry

Ananta K Gopalan

Jonathan Anisko

Robert P Sim

Kyle Earl Henry

A method and apparatus for separating particles from an inlet airflow of a turbine engine has a centerbody with a radially outer scavenge conduit. The inlet airflow has entrained particulate matter, which can impact an impact surface defining part of the centerbody. The impact surface can be disposed at an angle or have a low coefficient of restitution to reduce the velocity of the incoming particulate matter. The particulate matter is radially diverted radially outward through the scavenge conduit, unable to make a turn defined by the shape of the centerbody.

Inlet particle separator for a turbine engine

Embodiments of the present invention provide an inlet particle separator for a gas turbine engine having an inlet flow path, a scavenge flow path, a core flow path, and a flow splitter disposed between the scavenge and core flow paths. A plurality of grooves may be disposed about an inner surface of a wall of the separator within the inlet flow path.

Gas turbine engine particle separator

A fuel shield is configured for use in the afterburner of a turbofan aircraft engine. The shield includes wings obliquely joined together at a nose to conform with the leading edge region of a flameholder vane. A hood is joined to the wings and extends obliquely therefrom to conform with a supporting outer shell of the flameholder.

Purged flameholder fuel shield

A method facilitates assembling a gas turbine engine with a flameholder. The method comprises coupling at least one turning vane between a radially outer casing and a radially inner casing to form a flameholder, forming at least two slots that extend substantially radially through the outer and inner casings, coupling at least one fuel injector to the flameholder, and coupling the flameholder within the augmenter.

Method and apparatus for assembling a flameholder for an augmenter

A gas turbine engine rotor blade,includes a dovetail,and integral airfoil,. The airfoil includes a pair of sidewalls,extending between leading and trailing edges,, and longitudinally between a root,and tip,. The sidewalls are spaced laterally apart to define a flow channel,for channeling cooling air through the airfoil. The tip includes a floor,atop the flow channel, and a pair of ribs,laterally offset from respective sidewalls. The ribs are longitudinally tapered for increasing cooling conduction thereof.

Tapered tip-rib turbine blade

A cooled flameholder assembly includes a first heat shield having first and second spaced apart chambers. A fuel spraybar is disposed inside the first chamber, and a hollow baffle is disposed inside the second chamber. A second heat shield is joined to the first heat shield for closing the second chamber with the baffle therein. The baffle includes an inlet for receiving cooling air which is discharged through a plurality of outlet holes for impingement cooling the first and second heat shields.

Cooled spraybar and flameholder assembly including a perforated hollow

A cooled ignition flameholder assembly includes a first heat shield having first and second spaced apart chambers. A fuel spraybar is disposed inside the first chamber, and a hollow baffle is disposed inside the second chamber. A second heat shield is joined to the first heat shield for closing the second chamber with the baffle therein. The baffle includes an inlet for receiving cooling air which is discharged through a plurality of outlet holes for impingement cooling the first and second heat shields. An ignition bulb is disposed adjacent to the second chamber and receives an igniter tip and a fuel injector tip for initiating combustion.

Gas turbine engine ignition flameholder with internal impingement cooling

A cooling air transferring apparatus is provided particularly for transferring cooling air from hollow convergent flaps and seals to hollow divergent flaps and seals respectively in aircraft gas turbine engine variable nozzles. The preferred embodiment includes two semi-circular tubes, the first partially received within the second and both having a common center and radius of curvature so as to slide about the pivot point of the variable nozzle's pivotable convergent and divergent flaps and seals. The preferred embodiment further includes an entrainment opening on the second tube through which part of the first tube is received. The entrainment opening induces cooling air from the nozzle bay into the cooling air transfer tube to help cool the divergent flaps and seals.

Cooling air transfer apparatus for aircraft gas turbine engine exhaust

Means and method are disclosed for reducing buckling loads across an afterburner combustion liner in an augmented gas turbine engine. Means for accelerating bypass cooling airflow and then decelerating the accelerated bypass airflow for creating pressure losses to provide reduced-pressure bypass airflow to a plenum surrounding the afterburner liner are disclosed. In a preferred embodiment, the bypass airflow is accelerated to a velocity greater than Mach 1 and is then decelerated to a velocity less than Mach 1 for incurring shock waves for generating pressure losses for reducing differential pressure acting across the liner.

Means and method for reducing differential pressure loading in an

An inlet particle separator for a gas turbine engine is provided with unique vanes distributed around an entrance to a particle collection chamber. The vanes are uniquely constructed to direct extraneous particles that enter the engine into the collection chamber and prevent the particles from rebounding back into the engine's air flow stream. The vanes are provided with several features to accomplish this function, including upstream faces that are sharply angled towards air flow stream direction to cause particles to bounce towards the collection chamber. In addition, throat regions between the vanes cause a localized air flow acceleration and a focusing of the particles that aid in directing the particles in a proper direction.

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Swampscott, MA, United States of America

Jeffrey Carl Mayer